CN104632293B - Gas turbine blades - Google Patents
Gas turbine blades Download PDFInfo
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- CN104632293B CN104632293B CN201410609725.0A CN201410609725A CN104632293B CN 104632293 B CN104632293 B CN 104632293B CN 201410609725 A CN201410609725 A CN 201410609725A CN 104632293 B CN104632293 B CN 104632293B
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- China
- Prior art keywords
- end wall
- cooling
- gas
- cooling hole
- gas turbine
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
- F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
- F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/06—Fluid supply conduits to nozzles or the like
- F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/80—Platforms for stationary or moving blades
- F05D2240/81—Cooled platforms
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/202—Heat transfer, e.g. cooling by film cooling
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present invention provides a kind of cooling performance of end wall and the excellent gas turbine blades of the thermal efficiency of gas turbine.The gas turbine blades have in the internal blade part (310) with cooling flowing path (320), have in the end of the inner circumferential side of the gas-turbine radial direction of the blade part (310) in the gas turbine blades (300) of end wall (100), hook portion (110) setting cooling hole (130) in the blade inlet edge side of end wall (100), multiple cooling holes (130) are configured at different intervals along the circumferential direction of gas turbine, so as to which the cooling air (700) for flowing through cooling flowing path (320) and coming leads to from cooling hole (130) forward edge (101) effluent.
Description
Technical field
The present invention relates to the gas turbine blades for being used in gas turbine.
Background technology
The surface of gas turbine blades is exposed in the burning gases of high temperature, therefore in order to inhibit the high temperature of blade material rotten
Erosion, the decline of structural strength need forcibly to be cooled down to ensure viability.In recent years, in order to improve gas turbine
The thermal efficiency, and ignition temperature is made to increase, therefore the inner circumferential side end wall without the second level stator blade of cooling was also required to force in the past
Cooling.
As the document involved by the art, there are Japanese Unexamined Patent Publication 5-10102 bulletins (patent document 1).
Recorded in the bulletin " in the certain release to mainstream gas of cooling medium cooled down to blade parent (20a), but it is important
Be the end wall (20b) that the outlet (25) of cooling air is set to inner circumferential side blade inlet edge side position.”.In addition, note
It is loaded with that " outlet (25) is set to cavity (28) discharge to main stator blade (20) between the movable vane (1) in upstream side
Position.”.
" internal side diameter end wall (4b) is along week in addition, record in Japanese Unexamined Patent Publication 10-184312 bulletins (patent document 2)
To having the air flue (8) that is connected with the inside cooling flowing path of stator blade (2b) (7), ejiction opening (9) is relative to sealing fin
The front end of (16a) is located at mainstream side and in slit-shaped openings.”.Moreover, recording, " part for cooling air passes through setting
In the air flue (8) of internal side diameter end wall (4b), from the ejiction opening (9) of slit-shaped continuously in a circumferential towards second level movable vane body
The sealing fin (16a) of (11b) sprays.The cooling air being ejected is ejected in internal diameter side wall (4b) and sealing fin
The sealing device of the front end co-operating of (16a).At this point, by being diluted to the mainstream gas for leaking to a grade gap (25),
And bring the Wen Duxiajiang near sealing device.”.In addition, the reference numeral shown in above-mentioned parantheses is represented in each document
It is unrelated with the reference reference numeral of the aftermentioned present invention with reference to reference numeral.
Existing technical literature
Patent document
Patent document 1：Japanese Unexamined Patent Publication 5-10102 bulletins
Patent document 2：Japanese Unexamined Patent Publication 10-184312 bulletins
Invention content
In the gas turbine, air, and the sky that will have been compressed are sucked by the compressor being in gas-turbine on same axis
Gas is delivered to burner and it is made to mix to make fuel combustion with fuel.On the other hand, the cooling air of blade of gas turbine uses
A part of compressed air extracted from compressor.Therefore, the cooling air of blade of gas turbine is under the premise of cooling performance is maintained
Few as much as possible, improving the thermal efficiency of gas turbine needs compressed air for burning.
About the point, in Japanese Unexamined Patent Publication 5-10102 bulletins, about should be as from the viewpoint of the cooling of end wall
What by the outlet of the cooling air of the blade inlet edge side for the end wall for being configured at inner circumferential side along gas-turbine it is arranged circumferentially do not do it is any
It refers to.On the other hand, the air flue for being set to internal side diameter end wall of Japanese Unexamined Patent Publication 10-184312 bulletins is to cool down
Be configured at grade gap sealing device nearby and set, identically with document before, the viewpoint about the cooling from end wall
From the point of view of how along gas-turbine is arranged circumferentially should not to do any refer to.
The purpose of the present invention is to provide the combustions that a kind of cooling performance of end wall and the thermal efficiency of gas turbine are excellent
Blade of gas turbine.
The application includes multiple mechanisms for solving the above subject, if enumerating one example, a kind of gas turbine blades,
It is characterized in that, have：Blade part has cooling flowing path in inside；End wall is located at the gas-turbine of the blade part radially
A side end；Leading edge side hook, be for make the end wall with and the adjacent partition board engaging of the end wall hook portion, and position
In the front edge side of the blade part；And multiple cooling holes, it is set to the leading edge side hook and is connected with the cooling flowing path,
The multiple cooling hole exists adjacent cold in gas-turbine circumferential direction along gas-turbine circumferential array, and in multiple cooling hole
But it is spaced different cooling holes between hole.
In accordance with the invention it is possible to along gas-turbine in a manner that the necessity of the reinforcing cooling of each part with end wall is corresponding
It is circumferential suitably to distribute cooling air, therefore the usage amount of cooling air be inhibited, so as to improve the heat of gas turbine
Efficiency.
Description of the drawings
Fig. 1 is an example of the inner circumferential side end wall 100 of the gas turbine blades 300 of the first embodiment of the present invention
Vertical view.
Fig. 2 is the sectional view for carrying out cutting in face of gas turbine blades shown in FIG. 1 with the A-A ' in Fig. 1.
Fig. 3 is the side view of gas turbine blades 300 shown in FIG. 1.
Fig. 4 is the state for representing that seal gas is made to flow in the peripheral surface of the inner circumferential side end wall of gas turbine blades
Figure.
Fig. 5 is an example of the inner circumferential side end wall 100 of the gas turbine blades 300 of second embodiment of the present invention
Vertical view.
Fig. 6 is the sectional view for carrying out cutting in face of gas turbine blades 300 shown in fig. 5 with the B-B ' in Fig. 5.
Fig. 7 is an example of the inner circumferential side end wall 100 of the gas turbine blades 300 of third embodiment of the present invention
Vertical view.
Fig. 8 is the sectional view for carrying out cutting in face of gas turbine blades 300 shown in Fig. 7 with the C-C ' in Fig. 7.
In figure：100-inner circumferential side end wall, the leading edge of 101-end wall 100, the rear of 102-end wall 100,
110-upstream side hook (leading edge side hook), 120-downstream side hook (rear side hook), 130-cooling hole, 130a-entrance
Portion, 130b-outlet portion, 130c-middle part, 131-cooling hole, 131a-inlet portion, 131b-outlet portion, 131c-centre
Portion, 135-slot, 140-opening portion, 200-peripheral side end wall, 210-upstream side hook (leading edge side hook), 220-under
Swim side hook (rear side hook), 230-shock plate, 300-second level stator blade, 400-partition board, 410-hook, 500-first order
Movable vane, 600-second level movable vane, 700-cooling air, 710-seal gas, 720-it is exposed to the burning gases of high temperature
Region, 800-burning gases.
Specific embodiment
First, before various embodiments of the present invention will be described, to the gas turbine of the embodiments of the present invention
The main feature that blade is included illustrates.
(1) in the gas turbine blades of aftermentioned embodiments of the present invention, have：Blade part has in inside
Cooling flowing path；End wall is located at a side end of the gas-turbine radial direction of the blade part；Leading edge side hook (upstream side hook),
It is for make the end wall with and the end wall it is adjacent partition board engaging hook portion, and positioned at the blade part front edge side；
And multiple cooling holes, it is set to the leading edge side hook and is connected with the cooling flowing path, the multiple cooling hole is along gas
Turbine circumferential array, and in multiple cooling hole exist cooling hole adjacent in gas-turbine circumferential direction between interval not
Same cooling hole.
In the case of using the configuration method of above-mentioned cooling hole, if for example, in the gas-turbine circumferential direction of end wall,
The relatively high part of temperature concentrates cooling hole compared with other part, then passes through the cooling hole by using cooling air
Convection current cooling, using cooling air discharge from the cooling hole seal gas flow increase and temperature reduction, can
Preferential cooling is densely configured with the part of cooling hole, so as to being carried out along the situation of the circumferential equably configuration cooling hole of gas-turbine
Compare the cooling air volume that can be reduced and be discharged from each cooling hole.In other words, with being cooled down along the circumferential equably configuration of gas-turbine
The situation in hole compares the summation that can reduce the cooling air volume discharged from cooling hole, can reduce the rate of air sucked in required of compressed air,
Therefore it can inhibit the reduction of gas turbine proficiency.
(2) in addition, the Temperature Distribution of the gas-turbine circumferential direction of end wall is depended on from adjacent movable vane in gas-turbine axial direction
The seal gas flowed out with the gap (gap) of stator blade, that is, later along the surface of the gas passage side of the end wall of the stator blade
The flow of the seal gas of flowing.Therefore, positioned at the surface (gas of in the surface of above-mentioned end wall, above-mentioned blade part side
The surface of passage side) flowing seal gas the relatively less region (such as region 720 of aftermentioned Fig. 4) of flow in it is upper
State the arrangement pitch of the multiple cooling holes region (such as region 710 of aftermentioned Fig. 4) relatively more preferably than being located at the flow
In cooling hole arrangement pitch it is narrow.If cooling hole is configured as above, the flow for being capable of preferential coolant seal air is relatively fewer
High-temperature portion region, as a result can inhibit the reduction of gas turbine proficiency.
(3) in addition, in above-mentioned (2), so-called " the relatively small number of region of seal gas flow in end wall " is above-mentioned
Part near the leading edge of the above-mentioned blade part of end wall and from the part near the part to the abdomen side of above-mentioned blade part
Region (for example, it can be the region of the slave P1 to Pm of Fig. 1 later, in further area of the addition from P1 to Pb in the region
Domain).Therefore, by positioned at the arrangement pitch of above-mentioned multiple cooling holes in the region and other regions (for example, above-mentioned blade part
Region near back side) compared to being more densely packed configured, so as to effectively inhibit the reduction of gas turbine proficiency.
(4) shape as multiple cooling holes, can utilize variously-shaped, but for example there is following cooling holes.First, exist
In the state of above-mentioned end wall is fixed on aforementioned barriers portion via above-mentioned leading edge hook portion, cooling hole has：On being set to
State the inlet portion of the opening in face in the surface of leading edge hook portion, facing with above-mentioned cooling flowing path, as being set to above-mentioned leading edge
It the outlet portion of the opening in face in the surface of hook portion, opposed with aforementioned barriers and connects this in above-mentioned leading edge hook portion and enters
The hole of oral area and the outlet portion that is, the middle part of the outlet portion is extended to (for example, being equivalent to from the inlet portion towards front edge side
The cooling hole 130 of aftermentioned first embodiment).
In cooling hole as formed above, by entering in above-mentioned cooling hole from above-mentioned cooling flowing path via above-mentioned inlet portion
Cooling air above-mentioned end wall is cooled down first.Later, which discharges via above-mentioned outlet portion to before above-mentioned
The outside of edge hook portion reaches the above-mentioned of movable vane and stator blade by being formed in the gap between aforementioned barriers and above-mentioned end wall
Above-mentioned end wall is further cooled down during gap.Then, the cooling air in the gap and seal gas one are reached
With in release to gas passage.
(5) in the case where setting cooling hole as above-mentioned (4), can also further configured slot (for example, after being equivalent to
The slot 135 for the second embodiment stated), which is set to what in the surface of above-mentioned end wall, above-mentioned leading edge side hook protruded
Surface, and it is connected to from the above-mentioned outlet portion of above-mentioned cooling hole the leading edge potion of above-mentioned end wall.The slot, which is set to, " to be formed in above-mentioned
Gap between the engaging portion of partition board and above-mentioned end wall ", so even in the case of being small in the gap, cooling air
Because the slot there are due to easily by the gap, so as to improve cooling performance.
(6) in addition, other shapes as above-mentioned cooling hole, fix above-mentioned end wall via above-mentioned leading edge hook portion
In the state of aforementioned barriers portion, cooling hole has：As be set to it is in the surface of above-mentioned leading edge hook portion or above-mentioned end wall,
The inlet portion of the opening in face that is faced with above-mentioned cooling flowing path, above-mentioned end wall leading edge potion (in other words, in the end wall
In be located at burning gases circulating direction upstream side part) opening outlet portion and connect the inlet portion and the outlet
The hole in portion that is, from the inlet portion towards front edge side extend to the outlet portion middle part (for example, relative to aftermentioned third reality
Apply the cooling hole 131 of mode.).
By cooling hole as formed above, also can by the cooling air imported in above-mentioned cooling hole via above-mentioned inlet portion
Above-mentioned end wall is cooled down, the cooling air cooled down to above-mentioned end wall is in leading edge potion via above-mentioned outlet portion
It is identical with situation before near release to above-mentioned gap, it is finally discharged together with seal gas to gas passage.Therefore,
End wall can be cooled down even if cooling hole is formed as described above.
Hereinafter, the embodiments of the present invention are concretely demonstrated using attached drawing.The of gas turbine is enumerated herein
For two level stator blade 300, the inner circumferential of the inside of gas-turbine radial direction is located to the blade part 310 relative to the second level stator blade 300
The cooling construction of side wall portion 100 illustrates.
<First embodiment>
Fig. 1 is the one of the inner circumferential side end wall 100 of the gas turbine blades (stator blade) 300 of the first embodiment of the present invention
The vertical view of a example.Fig. 1 is (with reference to Fig. 2 from the inside of gas-turbine radial direction towards the figure of inner circumferential side end wall 100 from outside
Arrow I, I '), the stator blade (second level stator blade) 300 of present embodiment becomes is configured with two relative to an end wall 100
The two of blade part 310 connect blade.Fig. 1 shows an example of the configuration for the multiple cooling holes 130 for being set to hook portion 110,
There is the different cooling hole in the mutual interval of cooling hole adjacent in gas-turbine circumferential direction in multiple cooling holes 130.In addition, Fig. 2
It is the sectional view for carrying out cutting in face of gas turbine blades shown in FIG. 1 with the A-A ' in Fig. 1.Hereinafter, to using shown in FIG. 1
The reasons why configuration of cooling hole 130, illustrates.
Fig. 3 is the side view of gas turbine blades 300 shown in FIG. 1.In figure 3, the gas turbine leaf of present embodiment
Piece (second level stator blade) 300 has：Blade part 310, peripheral side end wall 200, upstream side hook 210, downstream side hook 220,
Inner circumferential side end wall 100, upstream side hook 110 and downstream side hook 120.
As shown in figure 3, the second level stator blade 300 of present embodiment is located in the upstream side of the flowing of burning gases 800
First order movable vane 500 and second level movable vane 600 in downstream side between.The burning gases come from the stream of first order movable vane 500
800 are accelerated in a manner of efficiently obtaining power by second level movable vane 600 by the blade part 310 of second level stator blade 300, and make stream
Dynamic direction deflection.In the second level, the end set of the inner circumferential side (gas-turbine radially inner side) of stator blade 300 has inner circumferential side end wall
100, there are peripheral side end wall 200, above-mentioned two end wall 100,200 in the end set of peripheral side (gas-turbine radial outside)
A part for the gas passage of gas turbine is formed, is consequently exposed in the burning gases of high temperature.
In peripheral side, end wall 200 is provided with positioned at the face (peripheral surface) of gas-turbine radial outside in partition board outer ring
(external partition) 450 fixes the upstream side hook (front edge side hook) 210 of peripheral side end wall 200 and downstream side hook (rear side hook)
220。
Upstream side hook 210 is protruded from the peripheral surface of end wall 200 towards gas-turbine radial outside, and front end has direction
The upstream side of the circulating direction (gas circulating direction) of burning gases is in the shape of the bond type of approximate right angle complications.On the other hand,
Downstream side hook 220 is protruded from the peripheral surface of end wall 200 towards gas-turbine radial outside, and front end is towards gas circulating direction
Downstream side in approximate right angle complications bond type shape.Two hook portions 210,220 rely on the bond type shape of the convex, with setting
Recess portion in partition board outer ring 450 engages, and the gas-turbine radial outside of second level stator blade 300 is fixed by two hook portions 210,220
In the shell (external partition 400) as meront.
On the other hand, it is provided with and is used for positioned at the face (inner peripheral surface) of gas-turbine radially inner side in inner circumferential side end wall 100
The upstream side hook (front edge side hook) 110 of inner circumferential side end wall 100 and downstream side hook are fixed in partition board inner ring (internal partition) 400
(rear side hook) 120.
Upstream side hook 110 is protruded from the inner peripheral surface of end wall 100 towards gas-turbine radially inner side, and front end has direction
The upstream side of gas circulating direction is in the shape of the bond type of approximate right angle complications.On the other hand, downstream side hook 120 is from end wall
100 inner peripheral surface is protruded towards gas-turbine radially inner side, but its front end is different from upstream side hook 110 not tortuous (wherein, can also
The front end for making downstream side hook 120 identically with upstream side hook 110 is tortuous).Partition board inner ring (internal partition) 400 is as upstream
Side hook 110 engage part and have hook portion 410.Hook portion 410 is dashed forward from the periphery of partition board 400 towards gas-turbine radial outside
The part gone out, front end have the shape in the bond type of approximate right angle complications towards the downstream side of gas circulating direction.As above shape
Into two hook portions 110,120 rely on convex shape, engage with the recess portion comprising the hook portion 410 for being set to partition board inner ring 400,
The partition board as meront is fixed on by two hook portions 110,120 so as to the gas-turbine radially inner side of second level stator blade 300
400。
As shown in Fig. 2, the cooling flowing path 320 for towards the inside for the blade part 310 for being formed in second level stator blade 300 flows
Cooling air 700 extracted from the compressor that is equipped on gas-turbine plant is (not shown), from the gas-turbine of blade part 310
Radial outside is supplied.Later, a part is discharged by the cooling flowing path 320 inside blade part 310 into gas passage,
Remaining cooling air flows to the cooling flowing path 320 of 400 side of partition board via the opening portion 140 for being set to inner circumferential side end wall 100.
In addition, cooling flowing path 320 shown in Fig. 2 becomes the linear flow path radially extended along gas-turbine, but do not limit
In this, well known shape can be utilized headed by the flow path shape radially circuitously advanced along gas-turbine in blade part 300.Separately
Outside, it is not illustrated herein with diagram, but from the flow adjustment orifice of partition board 400 is opened in wheel space stream after cooling air
After going out and wheel space being cooled down, upstream side is moved from gap 550, the downstream side with first order movable vane 500 from the second level
The gap 650 of leaf 600 is flowed out into gas passage, as prevent burning gases flow into wheel space seal gas play
Function.
In addition, in the example shown in Fig. 2, in peripheral side, the gas-turbine radial outside of end wall 200 is configured with shock plate
230, multiple impact openings (not shown) as pore are provided on shock plate 230.As by opposite from multiple impact opening
To carry out peripheral side end wall 200 construction of impinging cooling in the cooling air that the peripheral surface of peripheral side end wall 200 sprays.
Fig. 4 is shown from the outside of gas-turbine radial direction towards the surface (periphery from inside during the end wall 100 of inner circumferential side
Face), it is shown in an overlapping manner to the flow regime from the seal gas 710 with the outflow of the gap 550 of first order movable vane 500
The experimental result being observed.As shown in the drawing, seal gas 710 on the peripheral surface of inner circumferential side end wall 100 with deviation
Distribution flowing, part near the leading edge of each blade part 310 and from the part to the abdomen side of each blade part 310 near
The flow of seal gas 710 is opposite in partial region tails off.The region becomes the region for the burning gases for being exposed to high temperature
720, thus it is relatively low by the cooling effect of seal gas 710.Therefore, inventor etc. is found that in order to ensure inner circumferential side end wall
100 material viability and the cooling air volume imported in cooling flowing path 320 is reduced, emphasis, which is strengthened, is exposed to the burning of high temperature
This method of the cooling in the region 720 of gas is effective.Moreover, inventor etc. are by using in inner circumferential side end wall 100
Cooling multiple cooling holes 130 in region 720 and cooling hole positioned adjacent arrangement compared with other part more
It is intensive, it is cooled down so as to fulfill the reinforcing in the region 720.
Herein, Fig. 1 is returned.In Fig. 1, it is arranged at intervals in upstream side hook 110 along gas-turbine is circumferential across defined
Multiple cooling holes 130, multiple cooling hole 130 connect respectively with the cooling flowing path 320 in blade part 310.Multiple cooling holes 130
The arrangement pitch of gas-turbine circumferential direction be not all of identical, there are a different parts.Specifically, cooling hole 130 is configured to
The arrangement pitch for making gas-turbine circumferential direction in the region in region 720 for being equivalent to Fig. 4 is narrower than other parts.
As long as the seal gas of the region of the arrangement pitch of the constriction cooling hole 130 of gas-turbine circumferential direction based on shown in Fig. 4
Distribution determines, but there are following methods for the benchmark of the determining method as the region.That is, in the present embodiment, such as Fig. 1
It is shown, the position of the blade inlet edge of gas-turbine circumferential direction is set as point P1, the position of trailing edge is set as to point Pt, by point P1 with
The position that the center (midpoint) of point Pt is set as point Pm, connect in the face comprising gas-turbine central shaft with the back side of blade part 310
When being set as point Pb, make the arrangement pitch of cooling hole 130 included from point P1 to the region of point Pm narrower than other regions.Separately
Outside, can also be from the point P1 to the region of point Pm, the region constriction arrangement pitch also from point P1 to point Pb.
As shown in Figure 1 and Figure 2, each cooling hole 130 has：Inlet portion 130a, outlet portion 130b and connection inlet portion
The middle part 130c of 130a and outlet portion 130b.Inner circumferential side end wall 100 is being fixed on partition board inner ring via hook portion 110,120
In the state of 400, inlet portion 130a in the surface of upstream side hook 110, the face that faces with cooling flowing path 320 is open.Fig. 2
Inlet portion 130a be set to the root (Root portion) of the upstream side hook 110 relative to inner circumferential side end wall 100.
In the state of inner circumferential side end wall 100 is fixed on partition board inner ring 400 via hook portion 110,120, outlet portion 130b is in upstream side
Face opening in the surface of hook portion 110, opposed with the bond type of the hook portion 410 of partition board 400.Middle part 130C is in upstream side hook
The hole connected in portion 110 to inlet portion 130a with outlet portion 130b, and extended to from inlet portion 130a towards 101 side of leading edge
Outlet portion 130b.
In the second level stator blade 300 formed as described above, as shown in Fig. 2, the cooling air 700 extracted from compressor
It supplies from gas-turbine radial outside relative to second level stator blade 300, first, is sprayed from the impact opening on shock plate 230, it is right
Peripheral side end wall 200 is cooled down.Then, the cooling air in the inside cooling flowing path 320 by blade part 310 to blade
After portion 310 is cooled down, in part release to gas passage.In addition, it does not discharge to the remaining air of gas passage from cold
But flow path 320 flows into the flow path 330 of 400 side of partition board via opening portion 140, inside and external pressure differential using partition board 400,
And enter in cooling hole 130 from each inlet portion 130a of the surface opening in upstream side hook 110, by each cooling hole 130 from
Outlet portion 130b discharges.The cooling air released from each outlet portion 130b enters the inner circumferential for being formed in inner circumferential side end wall 100
Gap 150 (with reference to Fig. 3) between the peripheral surface of face and hook portion 410, towards before inner circumferential side end wall 100 in the gap 150
The direction movement of edge 101 (with reference to Fig. 1, Fig. 2), and released together with seal gas with the gap of first order movable vane 500 550
It puts.
As above it is cooled down by cooling hole 130 and the cooling air in gap 150 using convection current and to inner circumferential side end wall 100
It is cooled down.Particularly in the less region 720 of the flow of seal gas shown in Fig. 4, the arrangement pitch of cooling hole 130 with
Other regions enhance the convection current cooling capacity in region 720 compared to more intensive, and using in region 720
The flow of seal gas increases and temperature reduces and enhances cooling capacity, therefore can realize effective cooling.
If as above change cooling hole 130 gas-turbine circumferential direction arrangement pitch, can with inner circumferential side end wall 100
The corresponding mode of necessity of the reinforcing cooling of each section suitably distributes cooling air along gas-turbine is circumferential.It specifically, can
In the relatively less position of seal gas flow, cooling hole 130 is densely configured in (strengthening the higher position of the necessity of cooling)
And more distribute cooling air, on the other hand, can the relatively more position of seal gas flow (strengthen cooling must
The relatively low position of the property wanted) cooling hole 130 sparsely is configured and reduces the distribution of cooling air.Thus, for example being assumed to cool down
In the case that the sum of air total amount and cooling hole 130 is constant, according to the present embodiment, the arrangement pitch phase with cooling hole 130
Same situation is compared, and can reduce cooling air total amount.Thus, it is possible to reduce the amount of the compressed air extracted from compressor,
Therefore the thermal efficiency of gas turbine can finally be improved.
In addition, in the above example, the arrangement pitch of the gas-turbine circumferential direction of cooling hole 130 there is only two kinds, but according to
The distribution of seal gas flow can also utilize three kinds or more of arrangement pitch.
<Second embodiment>
In the present embodiment, the basis of the cooling hole 130 for the hook portion 110 being illustrated in the first embodiment
On, the slot 135 being connect with the cooling hole 130, the cooling hole 130 and the slot are set on the inner peripheral surface of inner circumferential side end wall 100
135 combinations strengthen cooling performance so as to increase cooling air volume.
Fig. 5 is the inner circumferential side end wall of the gas turbine blades (second level stator blade) 300 of second embodiment of the present invention
The vertical view of 100 example, and be the end wall 100 from the direction identical with Fig. 1 (with reference to arrow V, V of Fig. 6 ')
Figure.The figure shows an examples of the configuration of the slot 135 of the cooling hole 130 and end wall surface of hook portion 110.Fig. 6 is in Fig. 5
B-B ' in face of gas turbine blades 300 shown in fig. 5 carry out cutting sectional view.In Fig. 5 and Fig. 6, to have with
The part mark for the part identical function being explained in embodiment before is identical with embodiment before
Reference numeral simultaneously omits the description.
In the present embodiment, it is as shown in figure 5, circumferential along gas-turbine in the cooling hole 130 for being set to upstream side hook 110
It equally spaced arranges, and is provided with slot 135, slot 135 is set to the upstream side hook 110 in the surface of inner circumferential side end wall 100
Prominent surface (inner peripheral surface), and it is connected to from the outlet portion 130b of cooling hole 130 leading edge potion 101 of inner circumferential side end wall 100
Or near it.In addition, strengthen the cold of the region 720 (with reference to Fig. 4) that high-temperature portion is equivalent in inner circumferential side end wall 100 from realizing
But from the viewpoint of function, slot 135 be only arranged at Fig. 1 from point Pb to the outlet of cooling hole 130 that the region of point Pm is included
Portion 130b.
As shown in fig. 6, identically with embodiment before, even if in the present embodiment, inner circumferential side end wall 100
Upstream side hook 110 is also engaged with the upstream side hook 410 of partition board 400.Therefore, as in the prior embodiments, will be cold
But in the case that hole 130 is set to inner circumferential side end wall 100, if the inner circumferential side surface of the inner circumferential side end wall 100 and hook portion 410
Gap 150 (with reference to Fig. 3) it is relatively narrow, then the cooling air sprayed from the cooling hole 130 for being set to upstream side hook 110 is difficult to sometimes
It flows in 101 direction of forward edge.
Therefore, in the present embodiment, slot 135 in the inner circumferential side surface of inner circumferential side end wall 100 is set and expands cooling
The flow path width of air.Increased thereby, it is possible to spray the outlet from cooling hole 130 by the cooling air volume in gap 150.
As shown in figure 5, slot 135 is only arranged at identical with first embodimently positioned at straight near the blade inlet edge for needing to strengthen cooling
To the outlet side of the cooling hole 130 in the region of abdomen side.By above-mentioned construction, in addition to cooling air by cooling hole 130 with
And except convection current cooling effect during slot 135, additionally it is possible to increase the flow of the seal gas in the region with being flowed out from cooling hole 130
Cooling air, so as to strengthen the cooling in the region 720 for the burning gases for being exposed to high temperature (with reference to Fig. 4).As a result, energy
It is enough to distribute the cooling air delivery of inner circumferential side end wall 100 to required part, so as to inhibit cooling air delivery and carry
The thermal efficiency of high gas turbine.
In addition, in the present embodiment, though the arrangement pitch of the gas-turbine circumferential direction of cooling hole 130 is set as at equal intervals,
Also arrangement pitch can be made different as in the first embodiment, so as to the difference of further clear and definite assignment of traffic, and in realizing
The reinforcing cooling of side end wall 100.In addition, slot 150 can also be located at the outlet of whole cooling holes 130.
<Third embodiment>
In the present embodiment, cooling hole 130 is not set in upstream side hook 110, and mainly in inner circumferential side end wall 100
Inside setting cooling hole 131, to strengthen the cooling of required part.
Fig. 7 is the inner circumferential side end wall of the gas turbine blades (second level stator blade) 300 of third embodiment of the present invention
The vertical view of 100 example, and be from the direction identical with Fig. 1 and Fig. 5 (with reference to arrow VII, VII of Fig. 8 ')
The figure of end wall 100.The figure shows an examples of the configuration of cooling hole 131.Fig. 8 is in face of Fig. 7 institutes with the C-C ' in Fig. 7
The gas turbine blades 300 shown carry out the sectional view of cutting.In fig. 7 and fig. 8 to have in embodiment before
The part of the identical function in the part that is explained marks the reference numeral identical with embodiment before and omission
Explanation.
In the present embodiment, as shown in figure 8, cooling hole 131 has：Inlet portion 131a, outlet portion 131b and centre
Portion 131c.Specifically, cooling hole 131 is perforated as follows, in upstream side, the root of 110, hook has inlet portion 131a,
It is open from the inlet portion by outlet portion 131b of the inside of inner circumferential side end wall 100 near leading edge 101.In this configuration, energy
Enough cooled down using the convection current cooling effect of cooling hole 131 from the inside of inner circumferential side end wall 100, thus cooling effect compared with
It is high.
In addition, as shown in fig. 7, cooling hole 131 is configured to strengthening cooling from needs identical with first embodimently
Blade inlet edge is nearby until the region 720 of abdomen side and its nearby interval of constriction gas-turbine circumferential direction.By above-mentioned construction, with
Embodiment before in the same manner, can increase the range of constriction arrangement pitch seal gas flow with from cooling hole
The cooling air of 131 outflows, also can further strengthen the cooling from the inside of inner circumferential side end wall 100, therefore can have
Effect strengthens the region 720 that cooling is exposed to the burning gases of high temperature.
In addition, in the case that promoting the increased of the seal gas flow of inner circumferential side end wall 100 using cooling hole 131,
It is preferred that example as shown in Figure 8 the outlet portion 131b of cooling hole 131 is set to like that on the peripheral surface of inner circumferential side end wall 100
Near leading edge 101, and outlet portion 131b is made to be open towards the gas passage of gas turbine.If outlet portion 131b is set as above,
It is promptly flowed on the peripheral surface of end wall 100, therefore can easily increase from the cooling air that cooling hole 131 releases
The seal gas flow in the region 720 of high-temperature portion.
However, in the present embodiment, be compared with other embodiments, there are cooling hole 131 is elongated, cooling hole
The trend that the pressure loss inside 131 becomes larger, thus consider the reduction of cooling air volume, burning gases adverse current necessity ratio
Other embodiments are high, if but pay attention to above-mentioned point and apply, it can be by the cooling air delivery of inner circumferential side end wall 100
Distribution is to required part, so as to inhibit cooling air delivery and improve the thermal efficiency of gas turbine.
In addition, in the example shown in Fig. 8, though the inlet portion 131a of cooling hole 131 is set to 110, upstream side hook
Root, but if on the face faced with cooling flowing path 330 can also then be set in the part other than the root of 110, upstream side hook
Oral area 131a is placed in, oral area 131a can also be further set on the inner peripheral surface of inner circumferential side end wall 100.
In addition, the outlet portion 131b of cooling hole 131 can not only be set to the outer of inner circumferential side end wall 100 shown in Fig. 8
On circumferential surface, if can also then be set to other part near the leading edge potion 101 of inner circumferential side end wall 100.
However, in above-mentioned each embodiment, the complete cycle that the spreads all over gas-turbine arrangement cooling hole different to arrangement pitch
130th, 131 and the example of slot 135 be illustrated, but the degree of the cooling required according to end wall 100, can also be further
Specify the density of the arrangement of cooling hole 130,131 and slot 135 and only the circumferential part arrangement cooling hole 130 of gas-turbine,
131 and slot 135.For example, for each blade part, it can also be only in the area arrangement cooling hole of the slave Pb to Pm of Fig. 1
130, it is not provided with the structure of cooling hole 130 in other regions.
In addition, the section of cooling hole 130,131 illustrated respectively in above-mentioned each embodiment is the circle of predetermined radius
Shape, the section shape of long axis direction do not change, if but can be ensured that the outside of partition board 400 and internal pressure differential, and cool down empty
Gas is passed through with that can play the speed of the degree of the effect of cooling inner circumferential side end wall 100 and flow in cooling hole 130,131
In the range of, then it can suitably change the section shape of cooling hole 130,131.In addition, the axial direction for cooling hole 130,131
It is also identical for length.Also, in example (not shown), from the processing change made relative to the cooling hole 130,131 of stator blade 300
It is axially parallel with gas-turbine to have relative to upstream side hook 110 or inner circumferential side end wall 100 from the viewpoint of obtaining easily
The mode of central shaft cooling hole 130,131 is set, but is not limited to the direction, can also set and cool down along other directions
Hole 130,131.Above-mentioned point is also identical for slot 135.
In addition, in above-mentioned each embodiment, to the cold of the inner circumferential side end wall 100 of the second level stator blade of gas turbine
But it is illustrated, but also can be with the application of the invention, if being capable of profit for the inner circumferential side end wall of the stator blade of other grades
With the position of construction same as described above, then peripheral side end wall can be also further applied, applied to the quiet of steam turbine
The inner circumferential side of leaf and peripheral side end wall, applied to gas turbine and the movable vane of steam gas-turbine.
In addition, the present invention is not limited to above-mentioned each embodiment, the various changes not departed from the range of its purport are included
Shape example.For example, the present invention is not limited to have the whole compositions being illustrated in above-mentioned each embodiment, also include
Delete the composition of a part for its composition.It is other real alternatively, it is also possible to which a part for the composition of certain embodiment is appended to
It applies the composition of mode or is replaced as the composition of other embodiments.
Claims (4)
1. a kind of gas turbine blades, which is characterized in that have：
Blade part has cooling flowing path in inside；
End wall is located at a side end of the gas-turbine radial direction of the blade part；
Leading edge side hook, be for make the end wall with and the adjacent partition board engaging of the end wall hook portion, and positioned at described
The front edge side of blade part；And
Multiple cooling holes are set to the leading edge side hook and are connected with the cooling flowing path,
The multiple cooling hole exists adjacent in gas-turbine circumferential direction along gas-turbine circumferential array, and in multiple cooling hole
Cooling hole between the different cooling hole in interval,
A part for the cooling air only flowed into inside above-mentioned blade part is by being set to the above-mentioned cooling of above-mentioned leading edge side hook
Hole discharges,
It is relatively fewer with the flow of the seal gas of the surface flow of the blade part side in the surface of the end wall
The corresponding the multiple cooling hole in region arrangement pitch, the row of cooling hole more corresponding than region relatively large number of with the flow
Row interval is narrow,
It opens in the face faced with the cooling flowing path that the multiple cooling hole has respectively in the surface of the leading edge side hook
Mouthful inlet portion, as the face opposed with the partition board being set in the surface of the leading edge side hook opening outlet
Portion and the middle part for connecting the inlet portion and the outlet portion.
2. gas turbine blades according to claim 1, which is characterized in that
For the arrangement pitch of the gas-turbine circumferential direction of the multiple cooling hole,
With the part near the leading edge of the blade part of the end wall and from the part to the abdomen side of the blade part
The arrangement pitch of the corresponding the multiple cooling hole in region of neighbouring part, the arrangement of cooling hole more corresponding than with other regions
It is spaced narrow.
3. gas turbine blades according to claim 1, which is characterized in that
Slot is further equipped with, which is set to the surface that in the surface of the end wall, described leading edge side hook protrudes, and
The leading edge potion of the end wall is connected to from any of the multiple cooling hole outlet portion.
4. a kind of gas turbine, which is characterized in that
Have gas turbine blades described in claim 1.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
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| JP2013-230201 | 2013-11-06 | ||
| JP2013230201A JP6263365B2 (en) | 2013-11-06 | 2013-11-06 | Gas turbine blade |
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| CN104632293A CN104632293A (en) | 2015-05-20 |
| CN104632293B true CN104632293B (en) | 2018-06-29 |
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| US (1) | US9790799B2 (en) |
| EP (1) | EP2871323B1 (en) |
| JP (1) | JP6263365B2 (en) |
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| EP3052782B1 (en) * | 2013-10-03 | 2022-03-23 | Raytheon Technologies Corporation | Rotating turbine vane bearing cooling |
| US10451084B2 (en) | 2015-11-16 | 2019-10-22 | General Electric Company | Gas turbine engine with vane having a cooling inlet |
| US10876407B2 (en) * | 2017-02-16 | 2020-12-29 | General Electric Company | Thermal structure for outer diameter mounted turbine blades |
| JP7129277B2 (en) * | 2018-08-24 | 2022-09-01 | 三菱重工業株式会社 | airfoil and gas turbine |
| JP7451108B2 (en) | 2019-08-16 | 2024-03-18 | 三菱重工業株式会社 | Stator vanes and gas turbines equipped with them |
| CN111335967A (en) * | 2020-03-03 | 2020-06-26 | 清华大学 | Turbine static wheel disc, gas turbine and design method of end wall lateral outflow hole |
| JP7284737B2 (en) * | 2020-08-06 | 2023-05-31 | 三菱重工業株式会社 | gas turbine vane |
| JP2022061204A (en) * | 2020-10-06 | 2022-04-18 | 三菱重工業株式会社 | Gas turbine stator blade |
| CN113006880B (en) * | 2021-03-29 | 2022-02-22 | 南京航空航天大学 | Cooling device for end wall of turbine blade |
| CN113605994B (en) * | 2021-07-26 | 2023-10-03 | 中国船舶重工集团公司第七0三研究所 | Novel marine gas turbine low leakage loss duplex cooling guide vane structure |
| CN113803116B (en) * | 2021-09-18 | 2022-08-23 | 沈阳航空航天大学 | Turbine rotor blade with shrinkage type end wall film hole cooling structure |
| US11536143B1 (en) | 2021-12-22 | 2022-12-27 | Rolls-Royce North American Technologies Inc. | Endwall cooling scheme |
| US11635000B1 (en) | 2021-12-23 | 2023-04-25 | Rolls-Royce Corporation | Endwall directional cooling |
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| JPH0510102A (en) * | 1991-07-02 | 1993-01-19 | Hitachi Ltd | Gas turbine blade and gas turbine device |
| JP3997559B2 (en) * | 1996-12-24 | 2007-10-24 | 株式会社日立製作所 | gas turbine |
| DE59709701D1 (en) | 1997-09-15 | 2003-05-08 | Alstom Switzerland Ltd | Platform cooling for gas turbines |
| JPH11200807A (en) | 1998-01-12 | 1999-07-27 | Hitachi Ltd | Coolant recovery type gas turbine, and its stationary blade |
| JP3494879B2 (en) * | 1998-03-25 | 2004-02-09 | 株式会社日立製作所 | Gas turbine and gas turbine vane |
| DE19813779B4 (en) * | 1998-03-27 | 2005-04-14 | Rolls-Royce Deutschland Ltd & Co Kg | Arrangement for cooling the platforms of guide vanes of a gas turbine |
| FR2851287B1 (en) * | 2003-02-14 | 2006-12-01 | Snecma Moteurs | ANNULAR DISPENSER PLATFORM FOR TURBOMACHINE LOW PRESSURE TURBINE |
| DE102004029696A1 (en) | 2004-06-15 | 2006-01-05 | Rolls-Royce Deutschland Ltd & Co Kg | Platform cooling arrangement for the vane ring of a gas turbine |
| US7806650B2 (en) * | 2006-08-29 | 2010-10-05 | General Electric Company | Method and apparatus for fabricating a nozzle segment for use with turbine engines |
| EP1985806A1 (en) | 2007-04-27 | 2008-10-29 | Siemens Aktiengesellschaft | Platform cooling of a turbine vane |
| WO2009083456A2 (en) * | 2007-12-29 | 2009-07-09 | Alstom Technology Ltd | Gas turbine |
| US8118554B1 (en) | 2009-06-22 | 2012-02-21 | Florida Turbine Technologies, Inc. | Turbine vane with endwall cooling |
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| JP5506834B2 (en) * | 2012-01-27 | 2014-05-28 | 三菱重工業株式会社 | gas turbine |
| US9017013B2 (en) * | 2012-02-07 | 2015-04-28 | Siemens Aktiengesellschaft | Gas turbine engine with improved cooling between turbine rotor disk elements |
| CN102996187A (en) * | 2012-12-06 | 2013-03-27 | 哈尔滨汽轮机厂有限责任公司 | Combustion engine turbine first-level guide blade lower end wall cooling system |
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| Publication number | Publication date |
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| CN104632293A (en) | 2015-05-20 |
| EP2871323A1 (en) | 2015-05-13 |
| US9790799B2 (en) | 2017-10-17 |
| JP6263365B2 (en) | 2018-01-17 |
| US20150125310A1 (en) | 2015-05-07 |
| EP2871323B1 (en) | 2021-01-06 |
| JP2015090108A (en) | 2015-05-11 |
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